Research on Thermal Response Characteristics of Space Nuclear Power in High-Temperature and High-Velocity Impact Experiment under Accidental Reentry
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摘要: 高温高速撞击模拟试验是考核空间核反应堆异常再入大气层撞击地面事故安全性的重要项目。本文针对试验热加载和高速飞行阶段，建立了耦合传导、对流和辐射的有限体积模型，数值研究了试验中空间核反应堆堆芯模拟件的热响应特性，分析了加载温度变化速率和径高比的影响。结果表明，热加载阶段，堆芯模拟件最高温度和最低温度分别位于侧面及底面的交界处和模拟件中心；达到热平衡的时间除受加载温度变化速率的影响外还取决于模拟件径高比。高速飞行阶段，堆芯模拟件最高温度和最低温度所在位置与热加载阶段相反，且最低温度随着径高比和飞行时间的增加而减少。研究成果能够支撑高温高速撞击模拟试验系统研制及试验设计。
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关键词:
- 空间核反应堆 /
- 异常再入事故 /
- 高温高速撞击模拟试验 /
- 数值仿真 /
- 热响应特性
Abstract: High-temperature and high-velocity impact simulation test is a significant experiment to evaluate the safety of space nuclear power reactor in the accident impact on ground after accidental reentry. In this paper, a finite volume model coupling conduction, convection and radiation is established for the heat loading and high-velocity flight phase of the test, and the thermal response characteristics of the core simulator of the space nuclear reactor in the test are numerically studied, and the effects of loading temperature change rate and diameter-height ratio are analyzed. The results show that during the heat loading phase, the highest temperature and the lowest temperature of the core simulator are located at the junction of the side surface and the bottom surface and at the center of the simulator respectively. The time to reach thermal equilibrium is not only affected by the change rate of loading temperature, but also depends on the diameter-height ratio of the simulator. In the high-velocity flight phase, the highest and lowest temperatures of the core simulator are opposite to those in the heat loading phase, and the lowest temperature decreases with the increase of the diameter-height ratio and flight time. The research results can support the development and experimental design of high-temperature and high-velocity impact simulation test system. -
图 1 空间核反应堆异常再入高温高速撞击模拟试验系统示意图
Figure 1. Schematic Diagram of High-temperature and High-velocity Impact Simulation Test System for Space Nuclear Power Reactor in Accidental Reentry
图 2 堆芯模拟件截面温度随时间分布
r—堆芯模拟件径向长度；L—堆芯模拟件轴向长度
Figure 2. Temperature Distribution of the Reactor Core Simulator Cross-section versus Time
图 3 堆芯模拟件中心线温度演化规律
Figure 3. Temperature Evolution of Reactor Core Simulator Centerline
图 4 不同升温速率时堆芯模拟件最高温度和最低温度随时间的变化
Figure 4. Variation of Maximum and Minimum Temperatures of Reactor Core Simulator with Time under Different Loading Temperature Rates
图 5 不同升温速率时1200 K温度等值线随时间的变化规律
Figure 5. Variation of 1200 K Temperature Contour with Time under Different Loading Temperature Rates
图 6 不同径高比时堆芯模拟件最高温度和最低温度随时间的变化规律
Figure 6. Variation of Maximum and Minimum Temperatures of Reactor Core Simulator with Tme under Different Diameter-Height Ratios
图 7 不同径高比时1200 K温度等值线随时间的变化规律
Figure 7. Variation of 1200 K Temperature Contour with Time under Different Diameter-Height Ratios
图 8 高速飞行2 s时堆芯模拟件周围的温度场（上图）和速度场（下图）
Figure 8. Temperature Field (above) and Velocity Field (below) around the Reactor Core Simulator at t=2 s
图 9 高速飞行2 s时堆芯模拟件表面温度场
Figure 9. Surface Temperature Field of Reactor Core Simulator at t=2 s
图 10 堆芯模拟件最低温度随飞行时间变化规律
Figure 10. Variation of Minimum Temperature of Reactor Core Simulator with Time
表 1 计算参数设置
Table 1. Parameter Setting in the Simulation
参数 热加载阶段 高速飞行阶段 升温速率k/(K·h−1) 150/200/250 — 初始温度$ {T}_{0} $/K 300 1473 目标温度$ {T}_{\mathrm{f}\mathrm{i}\mathrm{n}} $/K 1473 >1373 径高比$ \varPhi /H $ 0.426/0.833/1.439 0.426/0.833/1.439 飞行速度
（或空气速度）$ {U}_{0} $/(m·s−1)— 90 空气温度$ {T}_{\mathrm{a}\mathrm{i}\mathrm{r}} $/K — 300 
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表 2 堆芯模拟件高速飞行阶段计算结果
Table 2. Numerical Results for the High-velocity Flight Phase of Reactor Core Simulator
算例 回流区长度/m $ {C}_{\mathrm{d}} $ f/Hz St $ \varPhi /H $=0.426 0.810 0.837 11.0 0.049 $ \varPhi /H $=0.833 0.840 0.855 9.8 0.054 $ \varPhi /H $=1.439 1.425 1.030 8.8 0.059
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